Flying-machine.



H. F. CUNTZ.

FLYING MACHINE.

APPLICATION man JUNE 25. 1910.

Patented July 25, 1916.

2 SHEETS-SHEET 1.

me vvlfoz wit messes I 7 11mm a. n.

H. F. CUNTZ.

FLYING MACHINE.

APPLICATION ms!) 1UNE25, 1910.

1 1 92,607 Patented July 25, 1916.

2 SHEETS-SHEET 2.

l/qhtmcooao mfw ms NORRIS pnzns cm. Pnaml.n|w.. wAsumcruN. n c

I-IERMANN F. GUNTZ, OF HARTFORD, CONNECTICUT.

FLYING-MACHINE.

Specification of Letters Patent.

Patented July 25, 1916..

Application filed June 25, 1910. Serial No. 568,776.

To all whom it may concern Be it known that I, HERMANN F. Cun'rz, acitizen of the United States, residing in the city and county ofHartford, State of Connecticut, have invented certain new and usefulImprovements in Flying-Machines, of which the following is aspecification.

My invention relates to heavier-than-air machines, which are flyingmachines propelled through the air and having planes or surfaces againstwhich the air impinges at a slight angle, and by the reaction againstthese planes or surfaces sustains the machine in the air.

Among the objects of my invention are means to effect lateral stability,as well as to restore stability or deflect the machine when turning, orunder other desired conditions, as well as other objects which willappear hereafter.

In the drawings illustrating embodiments of my invention. Figure 1 is afront view looking down on a biplane; Fig. 2 is a side view of themiddle portion showing the stabilizing-plane in its relation to the mainparts of the engine; Fig. 3 is the top of the stabilizing-plane andconnections; Fig. 4 is a front view of a monoplane; Fig. 5 is a sideelevation of the central portion of Fig. 4; Fig. 6 is a horizontalsection of the stabilizing plane; Fig. 7 is an end view of part ofstabilizing-plane.

In Figs. 1, 2 and 3, A is the stabilizingplane; B is a vertical memberto which the forward edge of the stabilizing plane A is secured; C isthe rear upright; D is the operating sleeve; E is an operating lever; Fa link; G bell-crank; H operating links; J operating foot-lever.

In connection with the stabilizing-plane, a is the upper slat; c is thelower slat; d are straps; e straps; f upper operating bar; f loweroperating bar; g upper operating sector; 9 lower operating sector; itoperating cords; 7c pivots for operating bar.

In Figs. 4, 5, 6 and 7, the same parts are designated by same letters asabove, with the addition of a central slat b, and at a a the doublearrangement of the slats is shown. The main parts of the machine areindicated as propeller 1; engine 2; seat 8; and in the biplane theplanes 4. and 4; and in the monoplane the supporting-plane 5; 6 6 6 arebraces.

My invention-will now be understood in connection with the followingdescription of the particular embodiments shown in the drawings, inwhich the upright B or stanchion projects above the plane or theuppermost plane of a biplane, and in front of the center of gravity ofthe entire machine. This is braced to resist the strains from windpressure and connected at the top by a bar with the rear stanchions orupright C. e

The stabilizing-plane A is secured by any suitable means, as straps d(l, to the post B, and the upper and lower slat a and c are strapped asat c to the horizontal bars connecting B and C, at a place near theforward end. At the rear of the slats connections are made whereby therear end may be deflected back and forth in order to warp the plane atthe will of the operator. 'Thls operating means includes the operat ingbars f and f, which are pivoted at 70 to the slats and project to eachside, and

have at their ends cords h attached, which are roved around theperiphery of sectors g and g, and at the corners of the sectors theropes it are made fast. These sectors are attached to the sleeve D whichsurround the rear post C and projects down to the convenient place nearthe level of the operator, and thereby levers E, links F, bell-crank Gand operating bars H may be operated by the aviator pushing on thefoot-lever J. The slats a, b and c are made flat and flexible so thatthey will yield sidewise and be otherwise stiff. Between the slats theplane is built-up of any suitable material, and the size of this plane Awill vary depending upon particular machine and conditions for flying.It will thus be seen that the aviator by means of a foot steering levercan deflect the rear end of the stabilizing-plane and warp it to anydegree he may desire. The upper sector 9 may be larger, as shown, thanthe lower sector 9, so that the turning of the sleeve D any given degreewill move the bar 7 farther from its normal position than the bar f. Anynumber of intermediate devices may be used between the upper and loweredges of the plane, so as to warp the plane to the form desired, and thesize of these sectors or other operating means will be made to suit therequirements.

In the use of my invention it becomes unnecessary to deflect the lateralextremities of the horizontal planes 4 and 5, and these mainsupporting-planes can therefore be made with stiffness and rigiditysuitable for the purpose of supporting the load.

above the center of gravity and in position normally constituting aplane radial to the center of gravity and longitudinal of the machineand substantially vertical. By warping this plane, the effect is theapproach to a section of a helicoidal surface of very long pitch, whilethe longitudinal axis of the flying machine passing through the centerof gravity is substantially the center about which the warped surfacegenerates. In this manner the stabilizing-plane acts as a screw, when itis warped to one side or the other, and tends to turn the flying machineabout itslongitudinal axis, be cause the center of reaction on thestabilizing-plane is in such a position that it will have no tendency todeflect either the rear or the front of the machine laterally;

In Figs. 2 and 5, X indicates, in a general way the vertical linethroughthe center of gravity of the machine and the average center ofresistance of the stabilizing-plane,

from which it will be seen that the reaction, when the plane is suitablyarranged with respect to the machine as a whole, will only have theeffect of rotating the machine around its longitudinal axls and not anyeffect of turning it about a vertical axis,

which latter would be the case if the plane were placed in the front orrear, and under the latter conditions it would act as a rudder.

, In Fig. 1', the construction of biplane affords more suitable meansfor adapting two planes AA by continuing the uprights or struts betweenthe two main planes,which can then be suitably braced by stays 6, 6,tying the members together with the main body of the aeroplane so thatthe reaction on the planes will be transmitted properly throughout thestructure. planes, as shown, they do not radiate from the longitudinalaxis through the center of the flying machine. but it well above thecenter of gravity and'the center of buoyancy, and properly locatedlongitudinally, will produce the desired effect.

By the use of my invention all the operat- I ing mechanism forstabilizingis kept near the center of the machine, eliminating thenecessity of rigging carried to the extremities of the horizontal planesfor warping them. 'Furthermore, my stabilizing-plane With the doubleJune, 1910.

beingin' a vertical or substantially vertical position would be strainedonly when'deflected and would not be under the constant strain of ahorizontal warping plane. Furthermore, having the stabilizing-planeabove theoperator of the machine, would reduce the liability ofcrippling the machine as compared with embodiment of flexible wingedtips which are the first parts of the machine to engage an obstacle.

It will be evident that various modifications of my invention may bemade other than the particular form shown and described herein, but VWhat I claim and desire to secure by Letters Patent is: I

1. In a flying machine, fixed horizontal supporting planes, a verticalstabilizing plane section in a vertical line above the longitudinal axisof the machine, and above the supporting planes and means for adjustingsaid vertical plane section back of its forward edge, means embodied inthe construction of said plane and in the deflecting adjustment thereof,whereby a helical or screw surface is produced upon the deflection ofthe same, and with relation to the axis of the flying machine and itscenter of gravity, and whereby the reaction of said stabilizing planewill have a tilting and no lateral deflecting action in the nature of arudder. V

2. In a flying machine, rigid substantially horizontal supportingplanes, planes in substantially vertical planes above the center ofgravity of the machine and disposed symmetrically about a vertical planethrough the longitudinal axis'of the machine,each of said stabilizingplanes having its forward portion flexibly secured and its rear portiondeflectable, and means for symmetrically deflecting said planes, as andfor the purpose described.

3. In a flying machine, a fixed horizontal supporting plane, verticalstanchions extending above said fixed supporting planes, laterallyinclined braces extending from the upper portion of said verticalstanchions to lateral membersof the supporting planes, a verticalstabilizing plane articulated to the forward stanchion, means to trussthe forward stanchion against longitudinal strain,

and means. cooperating with the rear stanchion to deflect the rear endof the stabilizing plane laterally with relation thereto, and meansaccessible to the occupant to effect such lateral deflection.

Signed at New York, this 22nd day of 7 HERMANN F. CUNTZ. Witnesses: Y 4

'DANIEL J. GUINAN, I-I. MUOHMOBE.

. Copies of this patent may be obtained for five cents each, byaddressing the Commissioner of Patents,

, Washington, D. 0.

